A numerical method for computing unsteady 2-D boundary layer flows
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Authors
Krainer, Andreas
Subjects
COMPUTATIONAL FLUID DYNAMICS
FINITE DIFFERENCE THEORY
INVISCID FLOW
PANEL METHOD (FLUID DYNAMICS)
PREDICTIONS
TWO DIMENSIONAL BOUNDARY LAYER
UNSTEADY FLOW
AIRFOILS
COST EFFECTIVENESS
DATA CORRELATION
EDDY VISCOSITY
REYNOLDS STRESS
FINITE DIFFERENCE THEORY
INVISCID FLOW
PANEL METHOD (FLUID DYNAMICS)
PREDICTIONS
TWO DIMENSIONAL BOUNDARY LAYER
UNSTEADY FLOW
AIRFOILS
COST EFFECTIVENESS
DATA CORRELATION
EDDY VISCOSITY
REYNOLDS STRESS
Advisors
Date of Issue
1988-12
Date
Dec 01, 1988
Publisher
Language
Abstract
A numerical method for computing unsteady two-dimensional boundary layers in incompressible laminar and turbulent flows is described and applied to a single airfoil changing its incidence angle in time. The solution procedure adopts a first order panel method with a simple wake model to solve for the inviscid part of the flow, and an implicit finite difference method for the viscous part of the flow. Both procedures integrate in time in a step-by-step fashion, in the course of which each step involves the solution of the elliptic Laplace equation and the solution of the parabolic boundary layer equations. The Reynolds shear stress term of the boundary layer equations is modeled by an algebraic eddy viscosity closure. The location of transition is predicted by an empirical data correlation originating from Michel. Since transition and turbulence modeling are key factors in the prediction of viscous flows, their accuracy will be of dominant influence to the overall results.
Type
Technical Report
Description
Series/Report No
Department
Organization
Unspecified Center
Identifiers
NPS Report Number
Sponsors
Funder
NASA ORDER C-80017-F; RTOP 582-01-11
Format
Citation
Distribution Statement
Approved for public release; distribution is unlimited.
Rights
This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.